Airfoil Tools
Search 1638 airfoils

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Your Reynold number range is 50,000 to 1,000,000. (set)

Airfoil database search

Search the 1638 airfoils available in the databases filtering by name, thickness and camber. Click on an airfoil image to display a larger preview picture. There are links to the original airfoil source and dat file and the details page with polar diagrams for a range of Reynolds numbers.

(goe443-il) GOE 443 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 443 airfoil Max thickness 5% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 43.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca001035-il) NACA 0010-35		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0010-35 airfoil Max thickness 10% at 50% chord Max camber 0% at 0% chord Max Cl/Cd 43.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca000834-il) NACA 0008-34		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0008-34 airfoil Max thickness 8% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 43 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(sc20503-il) NASA SC(2)-0503 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0503 airfoil (NASA TP-2969) Max thickness 3% at 32% chord Max camber 0.8% at 82% chord Max Cl/Cd 42.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca000834-il) NACA 0008-34		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0008-34 airfoil Max thickness 8% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 42.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(goe444-il) GOE 444 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 444 airfoil Max thickness 5.6% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 42.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe445-il) GOE 445 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 445 airfoil Max thickness 6.4% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 42.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe561-il) GOE 561 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 561 airfoil Max thickness 25% at 29.8% chord Max camber 10.2% at 29.8% chord Max Cl/Cd 42 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca16021-il) NACA 16-021		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 16-021 airfoil Max thickness 21% at 50% chord Max camber 0% at 0% chord Max Cl/Cd 42 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e378-il) EPPLER 378 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E378 ultralight airfoil Max thickness 4.1% at 7.8% chord Max camber 8.1% at 35.9% chord Max Cl/Cd 41 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database